Performance Chart

900
700
600
500
400
300
200
100
RE
Additional Payload (lbs)
800
F
FE O
R
O RE
N N
LY C
E
UH-1H with Lycoming T53-L-13B Engine and Metal Main Rotor Blades
OGE Hover Performance Improvement with BLR FastFin System
0
0
2000
4000
6000
8000
10000
12000
Density Altitude
BLR COMPANY FLIGHT TEST DATA
14000
16000
F
FE O
R
R
O
E
N N
LY C
E
RE
FAA-Approved Operator’s Manual Supplement
NASA / BLR Dual Tail Boom Strakes for:
Helicopter Models: UH-1F, UH-1P & TH-1F
with Lycoming T53-L-13B Engine
and Metal Main Rotor Blades
CHAPTER 7 – PERFORMANCE
NOTE ALL ITEMS REMAIN AS IN BASIC OPERATOR’S MANUAL EXCEPT THE FOLLOWING:
HOVER CEILING
MAXIMUM TORQUE POWER AVAILABLE (30 MINUTE OPERATION)
F
FE O
R
R
O E
N N
LY C
E
324 ROTOR/6600 ENGINE RPM
12000
0
-3
WANTED
10000
4000
o
-
2000
0
-2000
6000
9000
CORRECTION TABLE:
TORQUE CORRECTION PSI*
.4
.5
o
.4
.6
.8
1.0
o
1.4
2.1
2.8
3.5
o
2.4
3.6
4.8
6.0
o
4.0
6.0
8.0
10.0
-50 C
RE
-60 C
o
*When operating at or below 0 C increase the
calibrated torque determined from sheet 2 by the
amount shown in the table to determine torque
required. See example on sheet 2.
8000
7500
7000
5
H 0(
EI
O
G
G
E)
H
T
-F
EE
T
.3
ID
.2
10
2515
o
SK
0C
-40 C
50
9500
2
40
7000 7500 8000 8500 9000
GROSS WEIGHT - LB(OGE)
5
30
GROSS WEIGHT - LB
20
6500
8500
CALIBRATED TORQUE-PSI
-20 C
C
ENTER PRESSURE ALTITUDE
MOVE RIGHT TO FAT
MOVE DOWN TO SKID HEIGHT
MOVE LEFT, READ GROSS WEIGHT
TO HOVER = 8810 POUNDS
6000
40
METHOD
20
30
PRESSURE ALTITUDE = 10600 FEET
o
FAT = 10 C
SKID HEIGHT = 2 FEET
10
8000
MAXIMUM WEIGHT LIMIT (9000 LB)
KNOWN
0
T
FA
PRESSURE ALTITUDE - FEET
GROSS WEIGHT TO HOVER
FAT
-2 -4 0
0
-1
0
BLR Hover Ceiling Sheet 1 Strake Only UH-1F Rev IR1.JNB
EXAMPLE
6500
6000
FIGURE A-5 Hover Ceiling Max Torque Available (30 min)
USAF UH-1F, UH-1P & TH-1F with Lycoming T53-L-13B Engine and Metal Main Rotor Blades
2
Document No. RFMS-BH205-10
FAA-Approved May 8, 2007
RE
F
FE O
R
R
O
E
N N
LY C
E
RE
F
FE O
R
R
O
E
N N
LY C
E
RE
F
FE O
R
R
O
E
N N
LY C
E
CM
MY
CY
C
M
CMY
Y
K